CN111822650B - Casting forming method for turbine guide blade of engine - Google Patents
Casting forming method for turbine guide blade of engine Download PDFInfo
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- CN111822650B CN111822650B CN202010856688.9A CN202010856688A CN111822650B CN 111822650 B CN111822650 B CN 111822650B CN 202010856688 A CN202010856688 A CN 202010856688A CN 111822650 B CN111822650 B CN 111822650B
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- shell
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C3/00—Selection of compositions for coating the surfaces of moulds, cores, or patterns
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/12—Treating moulds or cores, e.g. drying, hardening
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/22—Moulds for peculiarly-shaped castings
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- Engineering & Computer Science (AREA)
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Abstract
The invention relates to a casting forming method of an engine turbine guide blade, which comprises the following steps: preparing self-curing slurry by adopting fused quartz sand, acicular petroleum coke, silica sol and a curing material; coating self-curing slurry on the outer surface of the shell at a position corresponding to the tail end of the thin wall of the guide blade of the turbine of the engine; and naturally air-drying the shell, then pouring and smelting the alloy material into the shell into a liquid state, and obtaining the turbine guide blade of the engine after the alloy material is solidified. By adopting the technical scheme of the invention, the thickness of the shell in the area is increased by coating the self-curing slurry on the outer surface of the shell, when the alloy material which is smelted into liquid is poured into the shell, the heat dissipation speed of the area can be reduced, so that the difference between the heat dissipation speed of the area and the heat dissipation speed of other areas is reduced, the defects of under-casting and loosening in local positions are effectively prevented, the molding quality and the product qualification rate of castings are improved, and the frequency of repairing and processing the castings in the later period is avoided or reduced.
Description
Technical Field
The invention relates to the technical field of casting, in particular to a method for casting and forming an engine turbine guide blade.
Background
In the casting forming process, firstly, a shell is prepared according to the shape of a product, then a liquid metal material is poured and smelted into the shell, and the shell is cast and formed after the metal material is condensed, along with the continuous development of a casting process technology, the shape and the structure of a casting are more and more complex, when a turbine guide blade of an engine is cast and formed, the shape of the blade is a curved surface, the wall thickness is uneven, when the liquid metal material is poured and smelted into the pre-prepared shell, the heat dissipation speed of each part of the corresponding shell is uneven, so that the filling speed of the metal material is not consistent, the partial area is easy to have the situation of incomplete filling, so that the defect of under-casting is caused, the casting forming quality is influenced, the product percent of pass is not favorably improved, in addition, when the pouring temperature of the metal material is improved, the defect of looseness is easy to generate on the surface of the casting, and additional work polishing treatment is often required, the labor intensity of workers is increased.
Disclosure of Invention
In order to solve the technical problem, the invention provides a casting forming method of an engine turbine guide blade.
The invention provides a casting forming method of an engine turbine guide blade, which comprises the following steps:
the method comprises the following steps: preparing self-curing slurry: uniformly mixing fused quartz sand, acicular petroleum coke and silica sol according to the following mass parts, measuring the viscosity of the fused quartz sand, acicular petroleum coke and silica sol, and when the viscosity is 50-60 s, adding a proper amount of curing material and uniformly mixing to prepare self-curing slurry:
fused silica sand: 11 parts of (1);
needle petroleum coke: 5 parts of a mixture;
silica sol: 9 parts of (1);
curing the material: 2 parts of (1);
step two: preparing a shell according to the shape and the size of a pattern in a design drawing of the engine turbine guide blade provided by a user, painting a layer of self-curing slurry in the first step on the outer surface of the shell at a position corresponding to the end of the thin wall tip of the engine turbine guide blade, and naturally drying for a proper time;
step three: repeating the step two for a plurality of times, and naturally drying the shell for more than 20 hours for later use when the thickness of the self-curing slurry coating layer reaches 1/3-1/2 of the shell thickness;
step four: and pouring and smelting the alloy material in a liquid state into the shell, and obtaining the turbine guide blade of the engine after the alloy material is solidified.
The fused quartz sand in the step one is obtained by fusing the quartz sand screened by a 80-100-mesh screen.
In the first step, the silica sol is given the following grades: CRJ-30.
In the step one, the curing material is ammonium chloride.
And in the step one, the fused quartz sand, the acicular petroleum coke and the silica sol are uniformly mixed for 5-8 min.
And in the second step, the thickness of the self-curing slurry coated in each time is 3-5 mm.
And the thin-wall tip end of the engine turbine guide blade in the second step refers to a position where the wall thickness of the engine turbine guide blade is less than 0.78 mm.
And in the second step, the brushing tool of the self-curing slurry is a brush.
The invention has the beneficial effects that: by adopting the technical scheme of the invention, the self-curing slurry is coated on the position corresponding to the tail end of the thin wall of the guide blade of the turbine of the engine on the outer surface of the shell, so that the thickness of the shell in the area is increased, the self-curing slurry has good heat insulation capability, when the alloy material smelted into liquid is poured into the shell, the heat dissipation speed of the area can be reduced, the difference between the heat dissipation speeds of the area and other areas is reduced, the difference between the condensation speeds of the metal material in the poured metal material in the condensation process of each area is reduced, the defects of under-casting and loosening at local positions are prevented, the foundation is laid for improving the molding quality of castings, the qualification rate of finished castings is favorably improved, the frequency of repairing and processing the castings at the later stage is avoided or reduced, and the labor intensity of workers is reduced.
Drawings
FIG. 1 is a process flow diagram of the present invention;
figure 2 is a schematic of the construction of the shell of the present invention when coated with a self-setting slurry.
In the figure: 1-shell, 2-self-curing slurry.
Detailed Description
The technical solution of the present invention is further explained with reference to the accompanying drawings, but the claimed protection scope is not limited thereto;
the invention provides a method for casting and molding an engine turbine guide blade, which comprises the following steps as shown in figure 1:
the method comprises the following steps: preparing self-curing slurry 2: uniformly mixing fused quartz sand, acicular petroleum coke and silica sol according to the following mass parts, measuring the viscosity of the fused quartz sand, acicular petroleum coke and silica sol, and when the viscosity is 50-60 s, adding a proper amount of curing material and uniformly mixing to prepare self-curing slurry 2:
fused silica sand: 11 parts of (1);
needle petroleum coke: 5 parts of a mixture;
silica sol: 9 parts of (1);
curing the material: 2 parts of (1);
further, in the step one, the fused quartz sand is obtained by fusing the quartz sand screened by the 80-100-mesh screen. The preferred silica sol grades are: CRJ-30. The curing material is ammonium chloride. The fused silica sand, the acicular petroleum coke and the silica sol are uniformly mixed for 5-8 min.
Step two: preparing a shell 1 according to the shape and the size of a pattern in an engine turbine guide blade design drawing provided by a user, painting a layer of self-curing slurry 2 in the first step on the outer surface of the shell 1 at a position corresponding to the end of the thin wall tip of the engine turbine guide blade, and naturally air-drying for a proper time; in addition, the thickness of the self-curing slurry 2 coated in the second step is 3-5 mm each time. And in the second step, the thin-wall tip end of the turbine guide blade of the engine refers to the position where the wall thickness of the turbine guide blade of the engine is less than 0.78 mm. The brushing tool for the self-setting slurry 2 is a brush.
Step three: repeating the step two for a plurality of times, and naturally drying the shell 1 for more than 20 hours for later use when the thickness of the coating layer of the self-curing slurry 2 reaches 1/3-1/2 of the thickness of the shell 1;
step four: and (3) pouring and smelting the alloy material in a liquid state into the mould shell 1, and obtaining the turbine guide blade of the engine after the alloy material is solidified. By adopting the technical scheme of the invention, the overall dimension of the turbine guide blade of the engine is phi 265 multiplied by 24, each turbine of the engine needs to cast the guide blade, and when the technical scheme of the invention is put into production and application, only 1 casting with 32 pieces and under-casting defects is produced, the under-casting rate is only 3 percent, and the molding quality of the casting is greatly improved.
By adopting the technical scheme of the invention, the self-curing slurry is coated on the position corresponding to the tail end of the thin wall of the guide blade of the turbine of the engine on the outer surface of the shell, so that the thickness of the shell in the area is increased, the self-curing slurry has good heat insulation capability, when the alloy material smelted into liquid is poured into the shell, the heat dissipation speed of the area can be reduced, the difference between the heat dissipation speeds of the area and other areas is reduced, the difference between the condensation speeds of the metal material in the poured metal material in the condensation process of each area is reduced, the defects of under-casting and loosening at local positions are prevented, the foundation is laid for improving the molding quality of castings, the qualification rate of finished castings is favorably improved, the frequency of repairing and processing the castings at the later stage is avoided or reduced, and the labor intensity of workers is reduced.
Claims (6)
1. A method for casting and forming an engine turbine guide blade is characterized by comprising the following steps: the method comprises the following steps:
the method comprises the following steps: preparing self-curing slurry (2): uniformly mixing fused quartz sand, acicular petroleum coke and silica sol according to the following mass parts, measuring the viscosity of the fused quartz sand, acicular petroleum coke and silica sol, and when the viscosity is 50-60 s, adding a proper amount of curing material and uniformly mixing to obtain self-curing slurry (2): in the first step, the curing material is ammonium chloride;
fused silica sand: 11 parts of (1);
needle petroleum coke: 5 parts of a mixture;
silica sol: 9 parts of (1);
curing the material: 2 parts of (1);
step two: preparing a shell (1) according to the pattern shape and size in the design drawing of the engine turbine guide blade provided by a user, coating a layer of self-curing slurry (2) on the outer surface of the shell (1) corresponding to the thin-wall tip end of the engine turbine guide blade, wherein the thin-wall tip end of the engine turbine guide blade refers to the position where the wall thickness of the engine turbine guide blade is less than 0.78mm, and naturally drying for a proper time;
step three: repeating the step two for a plurality of times, and naturally drying the shell (1) for more than 20 hours for later use when the thickness of the coating layer of the self-curing slurry (2) reaches the thickness of 1/3-1/2 of the shell (1);
step four: and (3) pouring and smelting the alloy material in a liquid state into the shell (1), and obtaining the turbine guide blade of the engine after the alloy material is solidified.
2. The method of casting engine turbine guide vanes according to claim 1, wherein: the fused quartz sand in the step one is obtained by fusing the quartz sand screened by a 80-100-mesh screen.
3. The method of casting engine turbine guide vanes according to claim 1, wherein: in the first step, the silica sol is given the following grades: CRJ-30.
4. The method of casting engine turbine guide vanes according to claim 1, wherein: and in the step one, the fused quartz sand, the acicular petroleum coke and the silica sol are uniformly mixed for 5-8 min.
5. The method of casting engine turbine guide vanes according to claim 1, wherein: and in the second step, the thickness of the self-curing slurry (2) coated every time is 3-5 mm.
6. The method of casting engine turbine guide vanes according to claim 1, wherein: and in the second step, the brushing tool of the self-curing slurry (2) is a brush.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010856688.9A CN111822650B (en) | 2020-08-24 | 2020-08-24 | Casting forming method for turbine guide blade of engine |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010856688.9A CN111822650B (en) | 2020-08-24 | 2020-08-24 | Casting forming method for turbine guide blade of engine |
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| CN111822650A CN111822650A (en) | 2020-10-27 |
| CN111822650B true CN111822650B (en) | 2021-11-30 |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103231025A (en) * | 2013-04-18 | 2013-08-07 | 西安交通大学 | Preparation method of wall thickness controllable directional solidification casting mould |
| CN104318023A (en) * | 2014-10-27 | 2015-01-28 | 西安交通大学 | Method for controlling mixed crystal defects by locally thickening monocrystal blade shell on basis of simulation |
| CN104439097A (en) * | 2014-11-10 | 2015-03-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for solving penetrative porosity defect of high-temperature alloy expansion regulation sheet base plate |
| CN104690256A (en) * | 2015-02-11 | 2015-06-10 | 西北工业大学 | Directional solidification method for controlling foreign crystal defects of nickel-base superalloy step cast |
| CN107598097A (en) * | 2017-11-10 | 2018-01-19 | 东方电气集团东方汽轮机有限公司 | A kind of wax-pattern combination of turborotor and its fine casting method |
| CN109622888A (en) * | 2018-12-20 | 2019-04-16 | 航天海鹰(哈尔滨)钛业有限公司 | A kind of cast shaping process of the multi-joint guide vane casting of complexity high temperature alloy |
-
2020
- 2020-08-24 CN CN202010856688.9A patent/CN111822650B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103231025A (en) * | 2013-04-18 | 2013-08-07 | 西安交通大学 | Preparation method of wall thickness controllable directional solidification casting mould |
| CN104318023A (en) * | 2014-10-27 | 2015-01-28 | 西安交通大学 | Method for controlling mixed crystal defects by locally thickening monocrystal blade shell on basis of simulation |
| CN104439097A (en) * | 2014-11-10 | 2015-03-25 | 沈阳黎明航空发动机(集团)有限责任公司 | Method for solving penetrative porosity defect of high-temperature alloy expansion regulation sheet base plate |
| CN104690256A (en) * | 2015-02-11 | 2015-06-10 | 西北工业大学 | Directional solidification method for controlling foreign crystal defects of nickel-base superalloy step cast |
| CN107598097A (en) * | 2017-11-10 | 2018-01-19 | 东方电气集团东方汽轮机有限公司 | A kind of wax-pattern combination of turborotor and its fine casting method |
| CN109622888A (en) * | 2018-12-20 | 2019-04-16 | 航天海鹰(哈尔滨)钛业有限公司 | A kind of cast shaping process of the multi-joint guide vane casting of complexity high temperature alloy |
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| CN111822650A (en) | 2020-10-27 |
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